Results
72-19-02: 72-19-02 PITTS AVIATION ENTERPRISES, INC: Amdt. 39-1518. Applies to the Pitts Model S-2A Series Airplanes, S/N 2001 through 2025. Compliance required within the next 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent structural damage because of excessive in-flight vibration of the aileron interconnect tubes, accomplish the following: (a) Remove streamline aileron interconnect tubes, P/N 2-5216-1. NOTE: Make certain the length between the AN3 bolt centers for the upper and lower aileron attachments of the interconnect tube are not changed during removal. (b) Install round aileron interconnect tubes, P/N 2-5216-11. When installing the replacement tubes, make certain to adjust the length of the lower threaded end to the same overall length between AN3 bolt centers as the tubes originally installed on your airplane. Make certain that the correct number of AN960-10 (1/16 or 1/32 inch thick) washers are installed so that the bearing inner races are clamped-up snugly without bending the fork ends of the tubes. Pitts Service Bulletin No. 5, including Supplement No. 1, pertains to this same subject. This amendment becomes effective September 15, 1972.
2004-22-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires inspection of the metal oxide varistor (MOV) modules and transient absorption zener (TAZ) diodes to determine if those parts are outside of tolerance limits, and replacement of MOV modules and TAZ diodes with new parts, if necessary. This action is necessary to prevent the failure of critical ice protection systems following a lightning strike, which could result in reduced controllability and degraded performance of the airplane in the event of an encounter with icing conditions. This action is intended to address the identified unsafe condition.
2022-22-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 airplanes. This AD was prompted by a report that the path for the grounding wire of the engine fire shut off valve (FSOV) is routed through the wing trailing edge, which is not the shortest path available. This AD requires modifying the wiring between the inboard fixed leading edge in the wing and in the forward cargo compartment on the left- and right-hand sides, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2013-15-04: We are adopting a new airworthiness directive (AD) for certain Hartzell Propeller, Inc. propeller models HC-(1,D)2(X,V,MV)20-7, HC- (1,D)2(X,V,MV)20-8, and HC-(1,D)3(X,V,MV)20-8. This AD was prompted by failures of the propeller hydraulic bladder diaphragm and resulting engine oil leak. This AD requires replacement of the propeller hydraulic bladder diaphragm. We are issuing this AD to prevent propeller hydraulic bladder diaphragm rupture, loss of engine oil, damage to the engine, and loss of the airplane.
97-02-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Jetstream Model BAe ATP airplanes, that requires repetitive inspections to detect damage of the antenna mounting reinforcing plates and surrounding fuselage skin. If any damage is detected, the AD requires replacement of the reinforcing plate with a new reinforcing plate and/or repair of the surrounding fuselage skin, which would terminate the repetitive inspection requirements. This amendment is prompted by reports of corrosion found at the antenna reinforcing plates, which was caused by the ingress of water at the plates. The actions specified by this AD are intended to prevent such corrosion, which could result in reduced structural integrity of the fuselage pressure vessel.
99-26-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires repetitive general visual inspections of the power feeder cables, terminal strip, fuseholder, and fuses of the galley load control unit (GLCU) within the No. 3 bay electrical power center to detect damage; and corrective actions, if necessary. This amendment is prompted by an incident of no power to the aft galleys and two incidents of sparking sounds coming from the G3 galley due to damage of the No. 3 and 4 wire assembly terminal lugs and overheating of the power feeder cables on the G3 GLCU. The actions specified in this AD are intended to prevent such damage due to the accumulated effects over time from overheating of the power feeder cables on the G3 GLCU, which could result in smoke and fire in the G3 galley.
2004-22-05: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-300, -400, and -500 series airplanes. This AD requires inspecting for discrepancies of the fuselage skin under the dorsal fin assembly, and repairing if necessary. This AD is prompted by a report of an 18-inch crack found in the fuselage skin area under the blade seals of the nose cap of the dorsal fin due to previous wear damage. We are issuing this AD to find and fix discrepancies of the fuselage skin, which could result in fatigue cracking due to cabin pressurization, and consequent rapid in-flight decompression of the airplane fuselage.
92-15-12: 92-15-12 AEROSPATIALE: Amendment 39-8306. Docket No. 92-NM-31-AD. Applicability: Model ATR42-300 and -320 series airplanes on which Modification 1694 (Aerospatiale Service Bulletin ATR42-32-0021) has been accomplished and on which Modification 2063 (Aerospatiale Service Bulletin ATR42-32-0028) has not been accomplished, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent a gear-up landing, accomplish the following: (a) Within 6 months after the effective date of this AD, modify the nose landing gear (NLG) retraction control logic, and perform a functional test of the landing gear retraction manual override control, in accordance with Aerospatiale Service Bulletin ATR42-32-0028, Revision 3, dated February 12, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The modification and functional test shall be done in accordance with Aerospatiale Service Bulletin ATR42-32-0028, Revision 3, dated February 12, 1991, which includes the following list of effective pages: Page Number Revision Level Date 1-2, 11, 13-21 3 February 12, 1991 3-10, 12 1 February 23, 1990 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (e) This amendment becomes effective on September 8, 1992.
2022-21-15: The FAA is adopting a new airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH (DAI) Model DA 42, DA 42 NG, and DA 42 M-NG airplanes. This AD is prompted by mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a loose rudder T-yoke axle nut. This AD requires replacing the rudder T-yoke axle with an improved rudder T-yoke axle. The FAA is issuing this AD to address the unsafe condition on these products.
2022-21-02: The FAA is superseding Airworthiness Directive (AD) 2000-20- 15, which applied to certain Airbus SAS Model A300 and A300-600 series airplanes. AD 2000-20-15 required a high frequency eddy current (HFEC) inspection to detect cracking of the rear fittings of fuselage frame FR40 at stringer 27, and repetitive inspections or repair, as applicable. In lieu of accomplishing the repetitive inspections, AD 2000-20-15 provided a modification that would allow the inspection to be deferred for a certain period of time. This AD was prompted by cracking of the rear fittings of fuselage frame FR40 at stringer 27, and a determination that reduced compliance times are necessary. This AD removes airplanes from the applicability, and continues to require the actions in AD 2000-20-15, but at reduced compliance times, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.